Wave Drag Reduction Approach for Lattice Wings at High Speeds

  • E. Schülein
  • D. Guyot
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)


The investigations of the aerodynamic performance of new locally swept lattice wings include numerical simulations as well as wind tunnel measurements. The investigations were performed at free-stream Mach numbers from 2 to 6 for angles of attack varied from 0 to 10 degrees. The performance of the lattice wings was assessed on the basis of the zero-lift drag and lift-to-drag ratio. The numerical and experimental results show that the novel design of the lattice wings has distinct advantages in comparison to the conventional unswept configurations. Compared to conventional lattice wings the maximum benefit e.g. of the zero-lift total drag for the investigated locally swept lattice wings is of the order of 30%–40%.


Mach Number Drag Reduction Wave Drag Total Drag Wind Tunnel Model 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.


Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.


  1. [1]
    S.M. Belotzerkovsky et al., ”Reschetchatye Kryl’ya”, Moscow, Mashinostroeniye, 1985 (in Russian); see also: S.M. Belotzerkovsky et al., ”Wings with internal Framework,” Machine Translation, FTD-ID (RS) T-1289-89, Foreign Technology Div., 1987.Google Scholar
  2. [2]
    W.D. Washington and M.S. Miller, ”An Experimental Investigation of Grid Fin Drag Reduction Techniques”, AIAA Paper 93-0035, Jan. 1993.Google Scholar
  3. [3]
    G.M. Simpson and A.J. Sadler, ”Lattice Controls: A Comparison with Conventional, Planar Fins”, Missile Aerodynamics Meeting Proceedings RTO-MP-5, Paper 9, 1998, pp. pp. 9.1–9.11.Google Scholar
  4. [4]
    W.D. Washington and M.S. Miller ”Experimental Investigations of Grid Fin Aerodynamics: A Synopsis of Nine Wind Tunnel and Three Right Tests”,Missile Aerodynamics, Meeting Proceedings RTO-MP-5, Paper 10, 1998, pp. 10.1–10.13.Google Scholar
  5. [5]
    R.W. Kretzschmar and J.E. Burkhalter, ”Aerodynamic Prediction Methodology for Grid Fins”, Missile Aerodynamics Meeting Proceedings RTO-MP-5, Paper 11, 1998, pp. 11.1–11.11.Google Scholar
  6. [6]
    Ph. Reynier and E. Schülein, „Incorporation of an Actuator Disc for Lattice Wing Modeling in an Unstructured Navier-Stokes Solver ”, New Results in numerical and experimental fluid mechanics IV, edited by Ch. Breitsamter et al., Notes on Numerical Fluid Mechanics and Multidisciplinary Design, Volume 87, Springer, Berlin 2004, pp.132–139.Google Scholar
  7. [7]
    Ph. Reynier, J.-M. Longo and E. Schiilein, „Simulation of Missiles with Grid Fins Using an Actuator Disk”, Journal of Spacecraft and Rockets, Vol.43, No.1, Jan.-Feb. 2006, pp.84–91.CrossRefGoogle Scholar
  8. [8]
    E. Schülein, ”Wing for an Aircraft or Spacecraft”, US Patent No. 7 114 685 BlGoogle Scholar
  9. [9]
    D. Guyot „Experimentelle und numerische Untersuchung zum Einfluss der Lamellengeometrie auf die Leistung eines Hochgeschwindigkeitsgitterflügels, ” Diploma thesis, TU Berlin, February 2005 (in German).Google Scholar
  10. [10]
    E. Schiilein and D. Guyot, ”Novel High-Performance Grid Fins for Missile Control at High Speeds: Preliminary Numerical and Experimental Investigations”Innovative Missile Systems, Meeting Proceedings RTO-MP-AVT-135, Paper 35, 2006, pp. 35–1–35–26, RTO, Available from: Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2007

Authors and Affiliations

  • E. Schülein
    • 1
  • D. Guyot
    • 2
  1. 1.Institut für Aerodynamik und StrömungstechnikDLRGöttingenGermany
  2. 2.Institut für Strömungsmechanik und Technische AkustikTU BerlinBerlinGermany

Personalised recommendations